内燃机工程2025，Vol.46Issue(3)：107-116,10.DOI:10.13949/j.cnki.nrjgc.2025.03.012
异型孔的气膜冷却数值模拟
Numerical Simulation of Film Cooling of Shaped Holes
景雪娇 1曹杰 1查浩 1李白羽 1韩熙 1张威龙1
作者信息
- 1. 中国空气动力研究与发展中心 计算空气动力研究所,绵阳 621000
- 折叠
摘要
Abstract
The self-developed cell-vertex unstructured computational fluid dynamics software AENS was used for the numerical simulation of film cooling.With regard to the influence of boundary layer grid and near-hole zone grid on the accuracy of film cooling simulation and the difference in cooling efficiency of films with shaped holes under different blowing ratios,a standard single-hole film cooling model was adopted,and a comparative study was carried out to investigate the difference in cooling efficiencies of different boundary layer grids,different near-hole zone grids,and three types of holes,namely,cylindrical holes,fan-shoped holes and dustpan holes under different blowing ratios.The results show that the height of the first layer of the grid does not have a great influence on the simulation results.The grid of the near-hole area has a greater influence on the simulation results under lower blowing ratios,and the mesh generated by nesting two O-type blocks in the near-hole area has a better simulation result.Under higher blowing ratios,the fan-shaped holes and laid-back fan-shaped holes have a more obvious increase in the film cooling efficiencies of the near-hole area,compared with the cylindrical holes.The GE-E3 high-pressure turbine with film guide vane model was simulated,which proved that the self-developed software has the ability to calculate engineering examples with complex film-cooling structures.The practicality and accuracy of the self-developed software was verified.关键词
气膜冷却/数值模拟/网格/异型孔/吹风比Key words
film cooling/numerical simulation/grid/shaped hole/blowing ratio引用本文复制引用
景雪娇,曹杰,查浩,李白羽,韩熙,张威龙..异型孔的气膜冷却数值模拟[J].内燃机工程,2025,46(3):107-116,10.
